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In recent years, satellite communication has gained increased prominence and driving factors are the reliability, new design techniques and reduced cost. The onboard control system components of the satellite are subjected to high temperature, shock and vibration both during initial transport and launch, and also during periodical orbital corrections. These effects can introduce faults in the control systems mounted on the space vehicle. Use of hybrid assembly technology for reducing size, weight and cost is recommended in satellite systems and hence, providing redundant hardware (a common method of recovering from faults) is not feasible since it increases both space and weight.
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